EP 3905466 A1 20211103 - FAULT-TOLERANT POWER SYSTEM ARCHITECTURE FOR AIRCRAFT ELECTRIC PROPULSION
Title (en)
FAULT-TOLERANT POWER SYSTEM ARCHITECTURE FOR AIRCRAFT ELECTRIC PROPULSION
Title (de)
FEHLERTOLERANTE LEISTUNGSSYSTEMARCHITEKTUR FÜR DEN ELEKTRISCHEN ANTRIEB EINES FLUGZEUGS
Title (fr)
ARCHITECTURE DE SYSTÈME D'ALIMENTATION TOLÉRANT AUX PANNES POUR LA PROPULSION ÉLECTRIQUE DES AÉRONEFS
Publication
Application
Priority
US 202016862212 A 20200429
Abstract (en)
A fault-tolerant power system architecture for aircraft electric propulsion. The fault-tolerant systems continue to operate in the event of the failure of (or one or more faults within) some component. The fault-tolerant design enables the system to continue its intended operation, possibly at a reduced level, rather than failing completely, when some part of the system fails. When a turn-to-turn fault in an AC motor is detected, a motor controller will short three top or three bottom switches in the inverter together (effectively shorting the associated stator windings) to divert fault current from the motor windings to the motor controller, where cooling is available. Also, when a fault in or at the input to a motor controller is detected, the motor controller cuts off power to the motor by issuing a command that causes an upstream contactor with high-voltage DC bus input to open.
IPC 8 full level
H02H 7/08 (2006.01); B64D 27/24 (2006.01); H02P 25/22 (2006.01); H02P 29/024 (2016.01); H02P 29/028 (2016.01)
CPC (source: CN EP KR US)
B60L 3/0061 (2013.01 - KR); B60L 15/20 (2013.01 - KR); B60L 50/51 (2019.01 - KR); B60L 53/20 (2019.01 - KR); B64C 13/00 (2013.01 - US); B64D 27/24 (2013.01 - CN EP KR); H02H 7/0833 (2013.01 - CN); H02H 7/0838 (2013.01 - EP); H02M 1/32 (2013.01 - CN); H02M 7/48 (2013.01 - CN); H02P 5/68 (2013.01 - US); H02P 25/22 (2013.01 - EP); H02P 27/06 (2013.01 - CN KR US); H02P 29/024 (2013.01 - CN KR); H02P 29/0241 (2016.02 - US); H02P 29/0243 (2016.02 - EP); H02P 29/028 (2013.01 - CN EP); B60L 2200/10 (2013.01 - EP KR); B60L 2240/42 (2013.01 - KR); B60Y 2200/51 (2013.01 - KR); Y02T 10/64 (2013.01 - EP); Y02T 10/70 (2013.01 - EP); Y02T 10/7072 (2013.01 - EP); Y02T 10/72 (2013.01 - EP); Y02T 50/40 (2013.01 - EP); Y02T 50/60 (2013.01 - EP KR); Y02T 90/14 (2013.01 - EP)
Citation (search report)
- [XAYI] DE 10007777 A1 20010920 - MAGNET MOTOR GMBH [DE]
- [XAY] DE 102006012215 A1 20070920 - MTU AERO ENGINES GMBH [DE]
- [XAY] DE 102015207117 A1 20160114 - SIEMENS AG [DE]
- [A] DE 102011016336 A1 20121011 - AIRBUS OPERATIONS GMBH [DE], et al
Designated contracting state (EPC)
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR
Designated extension state (EPC)
BA ME
DOCDB simple family (publication)
US 11128251 B1 20210921; CN 113572380 A 20211029; EP 3905466 A1 20211103; JP 2021172335 A 20211101; KR 20210134234 A 20211109; TW 202211610 A 20220316
DOCDB simple family (application)
US 202016862212 A 20200429; CN 202110460212 A 20210427; EP 21170104 A 20210423; JP 2021064683 A 20210406; KR 20210054294 A 20210427; TW 110112403 A 20210406